GOE 776 AIRFOIL (goe776-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 776 AIRFOIL (goe776-il) Reynolds number: 100,000 Max Cl/Cd: 33.33 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe776-il-100000.txt Download as CSV file: xf-goe776-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 776 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4013 0.14311 0.13613 -0.0308 1.0000 0.2446
-13.500 -0.9512 0.05841 0.05050 -0.0541 1.0000 0.2423
-13.250 -1.0704 0.04984 0.04144 -0.0464 1.0000 0.2440
-13.000 -1.0027 0.05154 0.04344 -0.0487 1.0000 0.2493
-12.750 -0.9967 0.05061 0.04254 -0.0469 1.0000 0.2536
-12.500 -1.0447 0.04727 0.03901 -0.0407 1.0000 0.2568
-12.250 -1.0963 0.04467 0.03620 -0.0326 1.0000 0.2594
-12.000 -1.1501 0.04290 0.03420 -0.0225 1.0000 0.2614
-11.750 -1.0782 0.04344 0.03510 -0.0279 1.0000 0.2680
-11.500 -1.0948 0.04254 0.03418 -0.0222 1.0000 0.2717
-11.250 -1.1323 0.04146 0.03298 -0.0133 1.0000 0.2746
-11.000 -1.1772 0.04056 0.03192 -0.0028 1.0000 0.2769
-10.750 -1.1904 0.03968 0.03099 0.0030 1.0000 0.2806
-10.500 -1.1615 0.03969 0.03122 0.0029 1.0000 0.2860
-10.250 -1.1735 0.03910 0.03060 0.0086 1.0000 0.2902
-10.000 -1.1970 0.03820 0.02953 0.0159 1.0000 0.2944
-9.750 -1.1998 0.03747 0.02877 0.0201 1.0000 0.2990
-9.500 -1.1819 0.03740 0.02887 0.0215 1.0000 0.3043
-9.250 -1.1861 0.03687 0.02829 0.0259 1.0000 0.3095
-9.000 -1.2024 0.03599 0.02716 0.0321 1.0000 0.3147
-8.750 -1.1824 0.03580 0.02718 0.0329 1.0000 0.3201
-8.500 -1.1571 0.03557 0.02699 0.0324 0.9962 0.3276
-8.250 -1.1242 0.03494 0.02622 0.0301 0.9883 0.3365
-8.000 -1.0784 0.03496 0.02641 0.0264 0.9804 0.3450
-7.750 -1.0532 0.03427 0.02548 0.0254 0.9710 0.3545
-7.500 -1.0037 0.03432 0.02579 0.0213 0.9634 0.3628
-7.250 -0.9791 0.03378 0.02506 0.0208 0.9532 0.3725
-7.000 -0.9330 0.03363 0.02510 0.0172 0.9452 0.3809
-6.750 -0.9025 0.03328 0.02469 0.0160 0.9358 0.3908
-6.500 -0.8658 0.03292 0.02439 0.0141 0.9262 0.3996
-6.250 -0.8169 0.03268 0.02417 0.0099 0.9208 0.4107
-6.000 -0.8025 0.03224 0.02370 0.0119 0.9070 0.4186
-5.750 -0.7490 0.03208 0.02367 0.0073 0.9016 0.4292
-5.500 -0.7405 0.03162 0.02306 0.0102 0.8880 0.4380
-5.250 -0.6846 0.03148 0.02313 0.0055 0.8821 0.4479
-5.000 -0.6680 0.03101 0.02247 0.0071 0.8714 0.4583
-4.750 -0.6207 0.03085 0.02255 0.0039 0.8631 0.4671
-4.500 -0.5785 0.03019 0.02176 0.0013 0.8578 0.4797
-4.250 -0.5462 0.03012 0.02187 0.0008 0.8469 0.4875
-4.000 -0.5116 0.02968 0.02140 -0.0002 0.8386 0.4986
-3.750 -0.4589 0.02908 0.02088 -0.0040 0.8341 0.5091
-3.500 -0.4433 0.02905 0.02088 -0.0017 0.8207 0.5182
-3.250 -0.4053 0.02842 0.02023 -0.0030 0.8136 0.5290
-3.000 -0.3530 0.02790 0.01977 -0.0065 0.8091 0.5401
-2.750 -0.3509 0.02779 0.01960 -0.0020 0.7935 0.5495
-2.500 -0.2973 0.02736 0.01929 -0.0055 0.7878 0.5596
-2.250 -0.2933 0.02717 0.01898 -0.0014 0.7741 0.5708
-2.000 -0.2425 0.02685 0.01882 -0.0044 0.7663 0.5800
-1.750 -0.2206 0.02653 0.01842 -0.0030 0.7564 0.5919
-1.500 -0.1883 0.02640 0.01838 -0.0032 0.7448 0.6011
-1.250 -0.1489 0.02593 0.01784 -0.0043 0.7380 0.6133
-1.000 -0.1343 0.02603 0.01801 -0.0018 0.7233 0.6228
-0.750 -0.0924 0.02574 0.01770 -0.0033 0.7152 0.6341
-0.500 -0.0801 0.02575 0.01773 -0.0005 0.7017 0.6450
-0.250 -0.0375 0.02564 0.01763 -0.0021 0.6925 0.6553
0.000 -0.0254 0.02559 0.01756 0.0007 0.6802 0.6677
0.250 0.0165 0.02564 0.01765 -0.0008 0.6699 0.6770
0.500 0.0301 0.02554 0.01749 0.0018 0.6591 0.6906
0.750 0.0703 0.02577 0.01777 0.0006 0.6475 0.6990
1.000 0.0872 0.02559 0.01749 0.0027 0.6382 0.7136
1.250 0.1239 0.02600 0.01801 0.0020 0.6255 0.7210
1.500 0.1564 0.02597 0.01786 0.0018 0.6168 0.7336
1.750 0.1781 0.02634 0.01834 0.0032 0.6042 0.7430
2.000 0.2229 0.02650 0.01837 0.0012 0.5951 0.7526
2.250 0.2331 0.02675 0.01872 0.0044 0.5834 0.7649
2.500 0.2814 0.02710 0.01897 0.0018 0.5734 0.7722
2.750 0.2892 0.02721 0.01913 0.0053 0.5634 0.7866
3.000 0.3374 0.02771 0.01959 0.0027 0.5524 0.7923
3.250 0.3632 0.02805 0.01992 0.0034 0.5428 0.8035
3.500 0.3921 0.02835 0.02021 0.0037 0.5321 0.8127
3.750 0.4409 0.02889 0.02066 0.0006 0.5221 0.8187
4.000 0.4468 0.02900 0.02084 0.0045 0.5126 0.8335
4.250 0.5099 0.02943 0.02105 -0.0009 0.5027 0.8372
4.500 0.5383 0.03009 0.02187 -0.0010 0.4908 0.8452
4.750 0.5655 0.03004 0.02167 -0.0006 0.4829 0.8573
5.000 0.6108 0.03077 0.02249 -0.0037 0.4708 0.8621
5.250 0.6586 0.03094 0.02249 -0.0070 0.4611 0.8698
5.500 0.6766 0.03135 0.02298 -0.0055 0.4519 0.8812
5.750 0.7273 0.03160 0.02314 -0.0095 0.4411 0.8872
6.000 0.7433 0.03190 0.02342 -0.0077 0.4334 0.9007
6.250 0.7904 0.03226 0.02380 -0.0114 0.4219 0.9062
6.500 0.8279 0.03253 0.02395 -0.0132 0.4132 0.9160
6.750 0.8554 0.03293 0.02446 -0.0138 0.4030 0.9254
7.000 0.9062 0.03302 0.02431 -0.0180 0.3942 0.9329
7.250 0.9244 0.03360 0.02511 -0.0172 0.3845 0.9442
7.500 0.9741 0.03359 0.02488 -0.0213 0.3757 0.9517
7.750 0.9974 0.03423 0.02569 -0.0216 0.3664 0.9623
8.000 1.0412 0.03428 0.02563 -0.0250 0.3574 0.9704
8.250 1.0745 0.03479 0.02619 -0.0270 0.3487 0.9792
8.500 1.1135 0.03500 0.02639 -0.0299 0.3396 0.9877
8.750 1.1558 0.03530 0.02663 -0.0334 0.3312 0.9949
9.000 1.1774 0.03580 0.02724 -0.0336 0.3231 1.0000
9.250 1.1950 0.03585 0.02711 -0.0324 0.3175 1.0000
9.500 1.1926 0.03655 0.02789 -0.0283 0.3123 1.0000
9.750 1.1815 0.03728 0.02875 -0.0229 0.3071 1.0000
10.000 1.1866 0.03757 0.02899 -0.0197 0.3019 1.0000
10.250 1.2110 0.03777 0.02897 -0.0194 0.2966 1.0000
10.500 1.1825 0.03878 0.03022 -0.0113 0.2927 1.0000
10.750 1.1627 0.03955 0.03109 -0.0045 0.2886 1.0000
11.000 1.1629 0.03989 0.03138 -0.0005 0.2841 1.0000
11.250 1.1959 0.04011 0.03136 -0.0014 0.2786 1.0000
11.500 1.1514 0.04107 0.03252 0.0092 0.2763 1.0000
11.750 1.1080 0.04212 0.03370 0.0191 0.2738 1.0000
12.000 1.0784 0.04327 0.03494 0.0265 0.2704 1.0000
12.250 1.0875 0.04361 0.03520 0.0290 0.2659 1.0000
12.500 1.1203 0.04385 0.03527 0.0285 0.2609 1.0000
12.750 1.0664 0.04619 0.03784 0.0376 0.2585 1.0000
13.000 1.0138 0.04945 0.04131 0.0446 0.2555 1.0000
13.250 0.9795 0.05260 0.04459 0.0489 0.2518 1.0000
13.500 1.1021 0.04826 0.03971 0.0427 0.2452 1.0000
13.750 1.0181 0.05359 0.04543 0.0506 0.2433 1.0000
14.000 0.3230 0.15053 0.14364 0.0250 0.2687 1.0000
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